An investigation into the damage development and residual strengths of open-hole specimens in fatigue

Oliver J Nixon-Pearson*, Stephen R Hallett

*Corresponding author for this work

Research output: Contribution to journalArticle (Academic Journal)peer-review

31 Citations (Scopus)
359 Downloads (Pure)

Abstract

An extensive experimental program was carried out to investigate and understand the sequence of damage development throughout the life of open-hole composite laminates loaded in tension-tension fatigue. Quasi-isotropic carbon/epoxy laminates, with stacking sequence [452/902/-452/02]S, [45/90/-45/0]2S and [45/90/-45/0]4S were examined. These were selected on the basis that under quasi-static loading the [452/902/-452/02]S configuration exhibited a delamination dominated mode of failure whilst the [45/90/-45/0]2S and [45/90/-45/0]4S configurations showed a fibre dominated failure mode, previously described as "pull-out" and "brittle" respectively. Specimens were fatigue loaded to 1 × 106 cycles or catastrophic failure, which ever occurred first. A number of tests were interrupted at various points as the stiffness dropped with increasing cycles, which were inspected using X-ray computed tomography (CT) scanning. A static residual strength program was carried out for run-out specimens of each configuration.

Original languageEnglish
Pages (from-to)266-278
Number of pages13
JournalComposites Part A: Applied Science and Manufacturing
Volume69
Early online date24 Nov 2014
DOIs
Publication statusPublished - Feb 2015

Keywords

  • A. Carbon-fibre
  • B. Fatigue
  • B. Fracture
  • X-ray computed tomography

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